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GOE 285 AIRFOIL (goe285-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 285 AIRFOIL (goe285-il)
Reynolds number: 500,000
Max Cl/Cd: 89.29 at α=8.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe285-il-500000.txt
Download as CSV file: xf-goe285-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 285 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3762   0.08495   0.08259  -0.0364   1.0000   0.0413
  -8.500  -0.3802   0.08201   0.07969  -0.0368   1.0000   0.0422
  -8.250  -0.3984   0.07855   0.07630  -0.0369   1.0000   0.0434
  -8.000  -0.4482   0.02408   0.02090  -0.0725   0.9820   0.0393
  -7.750  -0.4664   0.03615   0.03280  -0.0698   0.9846   0.0385
  -7.500  -0.4538   0.02814   0.02414  -0.0724   0.9780   0.0370
  -7.250  -0.4313   0.02220   0.01737  -0.0741   0.9733   0.0362
  -7.000  -0.3976   0.01989   0.01468  -0.0761   0.9709   0.0363
  -6.750  -0.3697   0.01845   0.01301  -0.0764   0.9634   0.0366
  -6.500  -0.3370   0.01720   0.01157  -0.0775   0.9587   0.0369
  -6.250  -0.3083   0.01621   0.01042  -0.0777   0.9501   0.0373
  -6.000  -0.2766   0.01537   0.00944  -0.0783   0.9430   0.0379
  -5.750  -0.2488   0.01473   0.00868  -0.0782   0.9318   0.0384
  -5.500  -0.2202   0.01412   0.00796  -0.0781   0.9208   0.0388
  -5.250  -0.1927   0.01337   0.00709  -0.0778   0.9087   0.0392
  -5.000  -0.1665   0.01259   0.00624  -0.0773   0.8958   0.0398
  -4.750  -0.1403   0.01209   0.00569  -0.0768   0.8826   0.0405
  -4.500  -0.1138   0.01171   0.00526  -0.0763   0.8695   0.0412
  -4.250  -0.0872   0.01139   0.00486  -0.0758   0.8563   0.0421
  -4.000  -0.0608   0.01110   0.00449  -0.0752   0.8424   0.0431
  -3.750  -0.0342   0.01085   0.00416  -0.0747   0.8285   0.0442
  -3.500  -0.0077   0.01054   0.00380  -0.0742   0.8153   0.0458
  -3.250   0.0191   0.01030   0.00354  -0.0738   0.8028   0.0478
  -3.000   0.0461   0.01013   0.00331  -0.0734   0.7896   0.0501
  -2.750   0.0729   0.00994   0.00307  -0.0729   0.7753   0.0537
  -2.500   0.0999   0.00977   0.00290  -0.0726   0.7604   0.0606
  -2.250   0.1271   0.00963   0.00279  -0.0722   0.7452   0.0757
  -2.000   0.1544   0.00956   0.00268  -0.0719   0.7296   0.0889
  -1.750   0.1814   0.00948   0.00259  -0.0716   0.7131   0.0990
  -1.500   0.2086   0.00943   0.00249  -0.0712   0.6967   0.1068
  -1.250   0.2359   0.00940   0.00242  -0.0710   0.6818   0.1144
  -1.000   0.2631   0.00936   0.00234  -0.0707   0.6677   0.1231
  -0.750   0.2903   0.00934   0.00229  -0.0704   0.6540   0.1337
  -0.250   0.3444   0.00919   0.00219  -0.0699   0.6267   0.1747
   0.000   0.3710   0.00900   0.00215  -0.0696   0.6134   0.2331
   0.250   0.3941   0.00824   0.00216  -0.0691   0.6002   0.4909
   0.500   0.4079   0.00717   0.00229  -0.0657   0.5873   0.8669
   0.750   0.4571   0.00727   0.00242  -0.0696   0.5684   0.9776
   1.000   0.5106   0.00744   0.00245  -0.0751   0.5453   0.9955
   1.250   0.5483   0.00760   0.00245  -0.0772   0.5222   1.0000
   1.500   0.5726   0.00773   0.00247  -0.0764   0.5009   1.0000
   1.750   0.5967   0.00790   0.00250  -0.0756   0.4809   1.0000
   2.000   0.6208   0.00807   0.00256  -0.0747   0.4634   1.0000
   2.250   0.6449   0.00825   0.00263  -0.0739   0.4482   1.0000
   2.500   0.6690   0.00843   0.00272  -0.0731   0.4346   1.0000
   2.750   0.6929   0.00863   0.00283  -0.0723   0.4217   1.0000
   3.000   0.7175   0.00879   0.00293  -0.0715   0.4093   1.0000
   3.250   0.7419   0.00896   0.00304  -0.0708   0.3972   1.0000
   3.500   0.7661   0.00916   0.00316  -0.0700   0.3846   1.0000
   3.750   0.7901   0.00936   0.00329  -0.0692   0.3709   1.0000
   4.250   0.8383   0.00980   0.00357  -0.0677   0.3369   1.0000
   4.500   0.8623   0.01005   0.00372  -0.0669   0.3192   1.0000
   4.750   0.8862   0.01031   0.00389  -0.0662   0.3056   1.0000
   5.000   0.9108   0.01054   0.00407  -0.0655   0.2954   1.0000
   5.250   0.9352   0.01079   0.00428  -0.0649   0.2867   1.0000
   5.500   0.9595   0.01105   0.00449  -0.0643   0.2784   1.0000
   5.750   0.9842   0.01129   0.00470  -0.0637   0.2720   1.0000
   6.000   1.0090   0.01152   0.00492  -0.0631   0.2659   1.0000
   6.250   1.0329   0.01182   0.00517  -0.0625   0.2607   1.0000
   6.500   1.0582   0.01202   0.00540  -0.0620   0.2568   1.0000
   6.750   1.0831   0.01224   0.00564  -0.0615   0.2518   1.0000
   7.000   1.1069   0.01253   0.00590  -0.0609   0.2463   1.0000
   7.250   1.1316   0.01277   0.00616  -0.0603   0.2418   1.0000
   7.500   1.1566   0.01298   0.00640  -0.0599   0.2368   1.0000
   7.750   1.1802   0.01327   0.00668  -0.0592   0.2314   1.0000
   8.000   1.2045   0.01351   0.00695  -0.0587   0.2257   1.0000
   8.250   1.2286   0.01376   0.00721  -0.0581   0.2178   1.0000
   8.500   1.2521   0.01405   0.00750  -0.0575   0.2104   1.0000
   8.750   1.2752   0.01435   0.00779  -0.0568   0.1997   1.0000
   9.000   1.2982   0.01467   0.00807  -0.0561   0.1813   1.0000
   9.250   1.3066   0.01609   0.00899  -0.0534   0.1095   1.0000
   9.500   1.3184   0.01720   0.00995  -0.0511   0.0822   1.0000
   9.750   1.3286   0.01835   0.01089  -0.0487   0.0539   1.0000
  10.000   1.3415   0.01917   0.01167  -0.0465   0.0467   1.0000
  10.250   1.3542   0.01991   0.01243  -0.0442   0.0439   1.0000
  10.500   1.3653   0.02077   0.01332  -0.0419   0.0417   1.0000
  10.750   1.3780   0.02154   0.01416  -0.0399   0.0405   1.0000
  11.000   1.3899   0.02238   0.01507  -0.0379   0.0394   1.0000
  11.250   1.4001   0.02335   0.01612  -0.0358   0.0383   1.0000
  11.500   1.4078   0.02453   0.01735  -0.0337   0.0372   1.0000
  11.750   1.4121   0.02600   0.01889  -0.0314   0.0363   1.0000
  12.000   1.4124   0.02787   0.02085  -0.0292   0.0355   1.0000
  12.250   1.4203   0.02928   0.02235  -0.0278   0.0350   1.0000
  12.500   1.4267   0.03090   0.02406  -0.0266   0.0345   1.0000
  12.750   1.4314   0.03274   0.02599  -0.0254   0.0338   1.0000
  13.000   1.4346   0.03481   0.02816  -0.0245   0.0332   1.0000
  13.250   1.4360   0.03715   0.03058  -0.0237   0.0326   1.0000
  13.500   1.4358   0.03977   0.03329  -0.0231   0.0321   1.0000
  13.750   1.4337   0.04272   0.03632  -0.0227   0.0316   1.0000
  14.000   1.4290   0.04604   0.03973  -0.0225   0.0312   1.0000
  14.250   1.4214   0.04976   0.04354  -0.0225   0.0308   1.0000
  14.500   1.4112   0.05377   0.04763  -0.0224   0.0304   1.0000
  14.750   1.4089   0.05704   0.05100  -0.0225   0.0301   1.0000
  15.000   1.4092   0.06013   0.05419  -0.0229   0.0297   1.0000
  15.250   1.4083   0.06340   0.05756  -0.0233   0.0293   1.0000
  15.500   1.4067   0.06680   0.06105  -0.0238   0.0289   1.0000
  15.750   1.4047   0.07030   0.06464  -0.0244   0.0285   1.0000
  16.000   1.4028   0.07383   0.06825  -0.0251   0.0280   1.0000
  16.250   1.4008   0.07734   0.07184  -0.0257   0.0277   1.0000
  16.500   1.3991   0.08083   0.07540  -0.0264   0.0273   1.0000
  16.750   1.3981   0.08421   0.07882  -0.0270   0.0269   1.0000
  17.000   1.3977   0.08741   0.08206  -0.0275   0.0265   1.0000
  17.250   1.3996   0.08986   0.08451  -0.0273   0.0260   1.0000
  17.500   1.4015   0.09231   0.08700  -0.0269   0.0255   1.0000
  17.750   1.3995   0.09624   0.09105  -0.0283   0.0252   1.0000
  18.000   1.3977   0.10010   0.09503  -0.0297   0.0249   1.0000
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